Self-cooled orifice structure
A self-cooled orifice structure that may be for a combustor of a gas turbine engine, and may further be a dilution hole structure, includes a hot side panel, a cold side panel spaced from the hot side panel, and a continuous inner wall extending between the hot and cold side panels and defining an orifice having a centerline and communicating axially through the hot and cold side panels. A plurality of end walls of the structure are in a cooling cavity that is defined in-part by the hot and cold side panels and the inner wall. Each end wall extends between and are engaged to the hot and cold side panels and are circumferentially spaced from the next adjacent end wall. A plurality of inlet apertures extend through the cold side panel and are in fluid communication with the cavity, and each one of the plurality of inlet apertures are proximate to a first side of a respective one of the plurality of end walls. A plurality of outlet apertures extend through the hot side panel and are in fluid communication with the cavity, and each one of the plurality of outlet apertures are associated with an opposite second side of a respective one of the plurality of end walls.
1. A self-cooled orifice structure in a combustor, the self-cooled orifice structure comprising:
a hot side panel;
a cold side panel spaced from the hot side panel;
a continuous inner wall extending between the hot and cold side panels and defining an orifice having a centerline and communicating axially through the hot and cold side panels; and
a plurality of end walls in a cooling cavity that is defined in-part by the hot and cold side panels and the continuous inner wall, wherein each end wall of the plurality of end walls extend between and are engaged to the hot and cold side panels and are circumferentially spaced from the next adjacent end wall, and wherein a plurality of inlet apertures extend through the cold side panel and are in fluid communication with the cooling cavity with each one of the plurality of inlet apertures being proximate to a first side of a respective one of the plurality of end walls, and wherein a plurality of outlet apertures extend through the hot side panel and are in fluid communication with the cooling cavity with each one of the plurality of outlet apertures being associated with an opposite second side of the respective one of the plurality of end walls.
2. The self-cooled orifice structure set forth in claim 1 further comprising:
a continuous outer wall spaced radially outward from the inner wall and extending between and engaged to the hot and cold side panels.
3. The self-cooled orifice structure set forth in claim 2 , wherein the cooling cavity is substantially annular in shape.
4. The self-cooled orifice structure set forth in claim 3 , wherein each one of the plurality of end walls extend radially between and are engaged to the inner and outer walls.
5. The self-cooled orifice structure set forth in claim 1 , wherein each one of the plurality of outlet apertures is a film hole angled to create a film of cooling air in a common swirling, circumferential, direction about the centerline.
6. The self-cooled orifice structure set forth in claim 5 , wherein each end wall of the plurality of end walls is angled to assist in the swirling direction of the cooling air film.
7. The self-cooled orifice structure set forth in claim 1 , wherein each end wall of the plurality of end walls has a cooling passage communicating through the opposite second side and in fluid communication between the cooling cavity and a respective one of the plurality of outlet apertures.
8. The self-cooled orifice structure set forth in claim 1 further comprising:
a plurality of cooling nodes projecting into the cooling cavity from the hot side panel.
9. The self-cooled orifice structure set forth in claim 8 , wherein the plurality of cooling nodes extend between and are engaged to the hot and cold side panels.
10. The self-cooled orifice structure set forth in claim 1 further comprising:
a plurality of fins engaged to the inner wall and projecting laterally into the orifice, wherein each fin of the plurality of fins is spaced circumferentially from the next adjacent fin and longitudinally extends in a spiraling orientation.
11. A combustor comprising:
a liner disposed about an axis and defining in-part a combustion chamber located radially inward and a cooling plenum located radially outward, and wherein a first plurality of film holes are in the liner and are in fluid communication between the cooling plenum and the combustion chamber, and are orientated to create a first cooling air film across the liner in the combustion chamber; and
an orifice structure engaged to the liner and including a hot side panel defining in-part the combustion chamber, a cold side panel spaced from the hot side panel and exposed to the cooling plenum, a continuous inner wall extending between the hot and cold side panels and defining an orifice having a centerline and communicating axially through the hot and cold side panels with respect to the centerline, and a plurality of end walls in a cooling first cavity that is defined in-part by the hot and cold side panels and the inner wall, wherein each end wall of the plurality of end walls extend between and are engaged to the hot and cold side panels and are circumferentially spaced from the next adjacent end wall, and wherein a plurality of inlet apertures extend through the cold side panel and are in fluid communication between the cooling first cavity and the cooling plenum with each one of the plurality of inlet apertures being proximate to a first side of a respective one of the plurality of end walls, and wherein a plurality of outlet apertures extend through the hot side panel and are in fluid communication between the cooling first cavity and the combustion chamber with each one of the plurality of outlet apertures being associated with an opposite second side of the respective one of the plurality of end walls.
12. The combustor set forth in claim 11 , wherein the orifice structure has a continuous outer wall spaced radially outward from the inner wall and extending between and engaged to the hot and cold side panels.
13. The combustor set forth in claim 12 further comprising:
a shell located radially outward from the liner, and wherein a cooling second cavity is located between the liner and the shell and defined at least in-part by the liner, the shell and the outer wall, and the cooling plenum is located radially outward from the shell with respect to the axis.
14. The combustor set forth in claim 13 , wherein the cooling second cavity is isolated from the cooling first cavity by the outer wall.
15. The combustor set forth in claim 13 , wherein the orifice is a dilution hole.
16. The combustor set forth in claim 13 , wherein the orifice is an igniter hole.
17. The combustor set forth in claim 13 , wherein the plurality of outlet apertures is a second plurality of film holes orientated to create a second air film flowing in a circumferential direction about the orifice for cooling the hot side panel.
18. The combustor set forth in claim 17 , wherein the second plurality of film holes is at least one micro-circuit exit of a plurality of at least one micro-circuit exits, and each one of the at least one micro-circuit exit is spaced circumferentially from the next adjacent at least one micro-circuit exit of the plurality of at least one micro-circuit exits.
19. The combustor set forth in claim 11 , wherein the orifice structure includes a vascular engineered lattice structure in the cooling first cavity.
20. The combustor set forth in claim 11 , wherein the orifice structure includes a plurality of fins engaged to the inner wall and projecting laterally into the orifice, wherein each fin of the plurality of fins is spaced circumferentially from the next adjacent fin and longitudinally extends in a spiraling orientation.